2a952 Volume 5 Ures (2016)

59 Questions

Settings
Please wait...
2a952 Volume 5 Ures (2016)


Questions and Answers
  • 1. 
    (801) The control surfaces that provide the aerodynamic force to maintain attitude and directional control of the aircraft include the ailerons,
    • A. 

      Elevator, and control wheel

    • B. 

      Elevator, and rudder

    • C. 

      Elevator, and flaps

    • D. 

      Flaps, and slats

  • 2. 
    (801) Which control surfaces provide aircraft roll control?
    • A. 

      Ailerons and flight spoilers

    • B. 

      Ailerons and lower rudder

    • C. 

      Flight spoilers and rudder

    • D. 

      Ailerons and rudder

  • 3. 
    (801) For high speed aileron operation, what surfaces are used in conjunction with spoilers for roll control?
    • A. 

      Inboard ailerons only

    • B. 

      Inboard elevators only

    • C. 

      Outboard ailerons only

    • D. 

      Both inboard and outboard ailerons

  • 4. 
    (801) Snubbers protect the ailerons from wind gusts in miles per hour (mph) up to
    • A. 

      60 mph

    • B. 

      70 mph

    • C. 

      80 mph

    • D. 

      90 mph

  • 5. 
    (801) Pitch control of the aircraft about the lateral axis is accomplished by the
    • A. 

      Elevators

    • B. 

      Ailerons

    • C. 

      Rudders

    • D. 

      Spoilers

  • 6. 
    (801) Which aircraft surface provides aircraft yaw control about the vertical axis?
    • A. 

      Elevators

    • B. 

      Ailerons

    • C. 

      Spoilers

    • D. 

      Rudder

  • 7. 
    (802) What are leading-edge and trailing-edge flaps used for?
    • A. 

      Coordinated turns

    • B. 

      Aileron augmentation

    • C. 

      Landings and takeoffs

    • D. 

      Pitch and yaw maneuvers

  • 8. 
    (802) How many leading edge flap surfaces are there? 
    • A. 

      18

    • B. 

      22

    • C. 

      26

    • D. 

      30

  • 9. 
    (802) The priority valve permits flow only when hydraulic pressure in pounds per square inch (psi) exceeds
    • A. 

      2500 ±300 psi

    • B. 

      2500 ±500 psi

    • C. 

      2000 ±300 psi

    • D. 

      2000 ±500 psi

  • 10. 
    (802) The flap power package receives hydraulic pressure from the number
    • A. 

      One and number two hydraulic systems

    • B. 

      One and number four hydraulic systems

    • C. 

      Two and number four hydraulic systems

    • D. 

      Two and number three hydraulic systems

  • 11. 
    (802) What provides the electrical signal used for flap asymmetry control?
    • A. 

      Comparator units

    • B. 

      Flap power packages

    • C. 

      Control cables and linkages

    • D. 

      Flap position indicating system

  • 12. 
    (803) What is not included in the mechanical flight control system?
    • A. 

      Cables

    • B. 

      Torque tubes

    • C. 

      Push-pull tubes

    • D. 

      Electrically powered actuators

  • 13. 
    (803) What is not an advantage of the use of electro-mechanical actuators?
    • A. 

      Reduces noise

    • B. 

      Reduces weight

    • C. 

      Eliminates the need for hydraulic fluid

    • D. 

      Eliminates the need for electrical power

  • 14. 
    (804) What surface trims the aircraft about the pitch axis?
    • A. 

      Horizontal stabilizer

    • B. 

      Gear train

    • C. 

      Ailerons

    • D. 

      Flaps

  • 15. 
    (804) Release of either half of the stabilizer trim control switch will
    • A. 

      Damage the auxiliary drive

    • B. 

      Result in nose down travel

    • C. 

      Stop the actuator motion

    • D. 

      Result in nose up travel

  • 16. 
    (804) The stabilizer trim autopilot servomotor supplies power to move the stabilizer during
    • A. 

      Ground operation only

    • B. 

      High speed operation

    • C. 

      Low speed operation

    • D. 

      Autopilot operation

  • 17. 
    (804) What type of action does the actuator assembly convert rotary motion into for the purpose of controlling the stabilizer trim?
    • A. 

      Nose left or nose right motion

    • B. 

      Vertical motion

    • C. 

      Linear motion

    • D. 

      Rotary speed

  • 18. 
    (805) What flight control surface indicator is designed to display percentage of surface extension?
    • A. 

      Flap/slat position indicator

    • B. 

      Rudder trim position indicator

    • C. 

      Aileron trim position indicator

    • D. 

      Horizontal stabilizer trim position indicator

  • 19. 
    (805) Synchro position indicating systems convert mechanical shaft angles to
    • A. 

      Mechanical shaft degrees

    • B. 

      Electrical shaft degrees

    • C. 

      Mechanical signals

    • D. 

      Electrical signals

  • 20. 
    (805) What type of operating power is required by a selsyn position indicating system?
    • A. 

      26 VAC

    • B. 

      28 VDC

    • C. 

      115 VAC

    • D. 

      120 VDC

  • 21. 
    (805) The selsyn position indicating system transmitter consists of a circular resistance winding with three taps positioned
    • A. 

      45 degrees apart

    • B. 

      90 degrees apart

    • C. 

      120 degrees apart

    • D. 

      180 degrees apart

  • 22. 
    (805) How accurately the selsyn position indicator rotor follows the transmitter depends upon the
    • A. 

      Amplitude of the applied voltage

    • B. 

      Frequency of the applied voltage

    • C. 

      Spacing of the coils and taps

    • D. 

      Strength of the rotor magnet

  • 23. 
    (806) Manual pitch and roll axis attitude adjustments are allowed by the
    • A. 

      Flight control augmentation system (FCAS)

    • B. 

      Stability augmentation system (SAS)

    • C. 

      Flight management system (FMS)

    • D. 

      Flight control set (FCS)

  • 24. 
    (806) The flight control set (FCS) pitch axis must be engaged for selection of altitude hold (ALT HOLD) or
    • A. 

      Mach number hold (MACH HOLD)

    • B. 

      Tactical air navigation (TACAN)

    • C. 

      Navigation/localizer (NAV/LOC)

    • D. 

      Heading select (HDG SEL)

  • 25. 
    (807) All signals needed for proper flight control set (FCS) operation are processed by the FCS
    • A. 

      Controller

    • B. 

      Processor

    • C. 

      Control panel

    • D. 

      Status/test panel

  • 26. 
    (807) Which component provides all switch holding voltages to the flight control set (FCS) control panel?
    • A. 

      FCS controller

    • B. 

      FCS processor

    • C. 

      FCS status/test panel

    • D. 

      Horizontal position sensor

  • 27. 
    (807) What condition is required to engage the flight control set (FCS) pitch axis?
    • A. 

      Valid heading signal

    • B. 

      Turn knob must be in detent

    • C. 

      Valid selected gyro #1 and gyro #2 signals

    • D. 

      Series yaw damper system must be engaged

  • 28. 
    (807) What condition is not required for flight control set roll axis engagement?
    • A. 

      Valid heading signal

    • B. 

      Turn knob must be in detent

    • C. 

      Valid selected gyro #1 signal

    • D. 

      Valid selected gyro #2 signal

  • 29. 
    (807) The status/test panel (STP) allows maintenance personnel to initialize and step through flight control set tests which are controlled by
    • A. 

      Air data computer software

    • B. 

      Analog to digital conversion

    • C. 

      Flight control set processor software

    • D. 

      Flight control set controller software

  • 30. 
    (807) The secondary goal of the flight control set continuous built-in-test (CBIT) is to isolate failures to a particular line replaceable unit (LRU) and store the information in the flight control set
    • A. 

      Processor non-volatile memory

    • B. 

      Controller non-volatile memory

    • C. 

      Processor volatile random access memory

    • D. 

      Controller volatile random access memory

  • 31. 
    (808) All characters on the flight control set (FCS) status/test panel (STP) are the result of display words sent from the FCS
    • A. 

      Controller

    • B. 

      Processor

    • C. 

      Control panel

    • D. 

      Disengage annunciator

  • 32. 
    (808) The flight control set (FCS) status/test panel (STP) provides personnel with an interface to the FCS
    • A. 

      Disengage annunciator

    • B. 

      Control panel

    • C. 

      Processor

    • D. 

      Controller

  • 33. 
    (808) Which flight control set (FCS) status/test panel (STP) pushbutton switch allows personnel to record an indicated failure in memory?
    • A. 

      Right arrow (→)

    • B. 

      Left arrow (←)

    • C. 

      VERIFY

    • D. 

      POWER

  • 34. 
    (808) Which flight control set (FCS) status/test panel (STP) pushbutton switch allows personnel to repeat a test?
    • A. 

      POWER

    • B. 

      VERIFY

    • C. 

      Left arrow (←)

    • D. 

      Right arrow (→)

  • 35. 
    (809) The component that enables the flight crew to engage and disengage the flight control set (FCS) is the FCS
    • A. 

      Controller

    • B. 

      Processor

    • C. 

      Control panel

    • D. 

      Status/test panel

  • 36. 
    (809) Engagement of the control panel ROLL axis switch causes the flight control set (FCS) to maintain the aircraft in a wings-level condition and
    • A. 

      Maintain the prevailing pitch attitude

    • B. 

      Maintain the prevailing yaw attitude

    • C. 

      Hold the existing heading

    • D. 

      Hold the existing altitude

  • 37. 
    (809) When the control panel NAV LOC switch is in the ON position, the flight control set (FCS) automatically
    • A. 

      Flies down the glide slope beam path

    • B. 

      Navigates along the selected course

    • C. 

      Achieves Mach

    • D. 

      Gains altitude

  • 38. 
    (809) The flight control set (FCS) control panel LOC ARM/CAP and G/S ARM/CAP indicators are controlled by the FCS
    • A. 

      Controller

    • B. 

      Processor

    • C. 

      Control panel

    • D. 

      Status/test panel

  • 39. 
    (809) When a flight control set (FCS) mode select switch is switched ON, a 28 VDC
    • A. 

      Engage signal is sent to the flight control set processor

    • B. 

      Disengage signal is sent to the flight control set processor

    • C. 

      Engage signal is sent to the flight control set servo drum and bracket

    • D. 

      Disengage signal is sent to the flight control set servo drum and bracket

  • 40. 
    (809) How many degrees of rotation do the flight control set (FCS) controller thumbwheels have? 
    • A. 

      90°

    • B. 

      180°

    • C. 

      270°

    • D. 

      360°

  • 41. 
    (809) How many degrees of rotation does the flight control set (FCS) controller turn knob have? 
    • A. 

      90°

    • B. 

      180°

    • C. 

      270°

    • D. 

      360°

  • 42. 
    (810) The flight control set (FCS) uses one servo motor to move the ailerons and one to move the
    • A. 

      Slats

    • B. 

      Rudders

    • C. 

      Spoilers

    • D. 

      Elevators

  • 43. 
    (810) What provides the only mechanical connection from the flight control set (FCS) servo motor to the aircraft control cables?
    • A. 

      Horizontal position sensor

    • B. 

      Servo drum and bracket

    • C. 

      Jackscrew assembly

    • D. 

      Trim actuator

  • 44. 
    (810) The component that provides a drive voltage to the flight control set (FCS) trim actuator is the FCS
    • A. 

      Controller

    • B. 

      Processor

    • C. 

      Control panel

    • D. 

      Status/test panel

  • 45. 
    (810) The flight control set (FCS) horizontal position sensor (HPS) consists of a
    • A. 

      Trim actuator

    • B. 

      Jackscrew assembly

    • C. 

      Servo drum and bracket

    • D. 

      Linear variable differential transformer

  • 46. 
    (811) What is the maximum bank angle in the flight control set (FCS) heading hold mode?
    • A. 

      10 degrees

    • B. 

      15 degrees

    • C. 

      20 degrees

    • D. 

      25 degrees

  • 47. 
    (811) What is the maximum bank angle in the flight control set (FCS) heading select mode?
    • A. 

      10 degrees

    • B. 

      15 degrees

    • C. 

      20 degrees

    • D. 

      25 degrees

  • 48. 
    (811) The flight control set (FCS) tactical air navigation (TACAN) mode will not advance to capture until the
    • A. 

      Turn knob is in detent

    • B. 

      Turn knob is out of detent

    • C. 

      Glide slope (G/S) switch is on

    • D. 

      Navigation/localizer (NAV/LOC) switch is off

  • 49. 
    (811) A prerequisite for entering the flight control set (FCS) localizer (LOC) capture mode is a valid
    • A. 

      Radio altimeter signal

    • B. 

      Glide slope signal

    • C. 

      Air data signal

    • D. 

      Mach signal

  • 50. 
    (812) What is the flight control set (FCS) pitch attitude limit?
    • A. 

      10 degrees

    • B. 

      15 degrees

    • C. 

      20 degrees

    • D. 

      25 degrees

  • 51. 
    (812) Which is not a command input the flight control set (FCS) pitch loop?
    • A. 

      Mach hold signals

    • B. 

      Glide slope signals

    • C. 

      Altitude hold signals

    • D. 

      Heading hold signals

  • 52. 
    (812) Flight control set (FCS) altitude hold cannot be engaged if the vertical velocity is greater than
    • A. 

      3000 feet per minute

    • B. 

      2500 feet per minute

    • C. 

      2000 feet per minute

    • D. 

      1000 feet per minute

  • 53. 
    (812) What provides information to the flight control set processor (FCSP) to produce an error signal when the aircraft goes above or below the engaged Mach number?
    • A. 

      Radio altimeter

    • B. 

      Air data computer

    • C. 

      Glide slope receiver

    • D. 

      Inertial navigation unit

  • 54. 
    (812) The flight control set (FCS) glide slope mode will disengage when the beam has been captured if selecting
    • A. 

      Navigation/localizer

    • B. 

      Heading select

    • C. 

      Altitude hold

    • D. 

      Test

  • 55. 
    (812) The flight control set (FCS) pitch thumbwheels, Mach hold, and altitude hold are disabled in
    • A. 

      Glide slope capture mode

    • B. 

      Localizer capture mode

    • C. 

      Glide slope arm mode

    • D. 

      Localizer arm mode

  • 56. 
    (813) From any initial rudder position, the series yaw damper (SYD) can command a
    • A. 

      Maximum of four degrees left or right rudder deflection

    • B. 

      Minimum of four degrees left or right rudder deflection

    • C. 

      Maximum of six degrees left or right rudder deflection

    • D. 

      Minimum of six degrees left or right rudder deflection

  • 57. 
    (814) When is the parallel yaw damper system intended to be operated?
    • A. 

      Only during flight

    • B. 

      Only during flight and taxi

    • C. 

      Only during flight, takeoff, and landing

    • D. 

      During flight, taxi, takeoff, and landing

  • 58. 
    (814) The parallel yaw damper system can only be engaged when the series yaw damper (SYD) is
    • A. 

      Engaged

    • B. 

      Disengaged

    • C. 

      In test mode

    • D. 

      In standby mode

  • 59. 
    (814) Which component of the parallel yaw damper system provides the necessary signals to stabilize the aircraft in the yaw axis?
    • A. 

      Yaw damper control panel

    • B. 

      Plug-in modules

    • C. 

      Power supply

    • D. 

      Rate gyro